CN106762158A - For operating the system and method that discharge standard is maintained while gas turbine - Google Patents
For operating the system and method that discharge standard is maintained while gas turbine Download PDFInfo
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- CN106762158A CN106762158A CN201610743517.9A CN201610743517A CN106762158A CN 106762158 A CN106762158 A CN 106762158A CN 201610743517 A CN201610743517 A CN 201610743517A CN 106762158 A CN106762158 A CN 106762158A
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- Prior art keywords
- burner
- fuel
- compressor
- gas turbine
- turbine
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
- F01N3/00—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
- F01N3/08—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous
- F01N3/10—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous by thermal or catalytic conversion of noxious components of exhaust
- F01N3/105—General auxiliary catalysts, e.g. upstream or downstream of the main catalyst
- F01N3/106—Auxiliary oxidation catalysts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/51—Inlet
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/08—Purpose of the control system to produce clean exhaust gases
- F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Materials Engineering (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Toxicology (AREA)
Abstract
The system and correlation technique of discharge standard are maintained while there is disclosed herein one kind for operating gas turbine (12) in downward pattern.System includes gas turbine (12), and it includes compressor (18), burner (26), turbine (30) and discharge section (38).Burner (26) is including being positioned at the multiple axially staged fuel injector (120) of multiple main fuel spray nozzles (104) and central fuel nozzle (102) downstream.Gas turbine (12) also include deflating (20) extract mouth (50), at least one of it is with compressor (18), compressor discharge housing (52) or burner (26) is in fluid communication.System also includes controller, and it is programmed for the air (20) and the multiple axially staged fuel injectors (120) of excitation from (20) extraction mouth (50) releasing compression of deflating during the downward of gas turbine (12) is operated.
Description
Cross-Reference to Related Applications
This application claims the power of the submission date of the U.S.Provisional Serial 62/210,636 of submission on the 27th of August in 2015
Benefit, during the application is incorporated herein by reference with it.
Technical field
The present invention relates generally to gas turbine generating factory, such as with vapour source and dry low NOx (DLN: Dry Low
NOx) combined cycle of combustion system or combined heat and power power plant.More particularly, the present invention relate in the pattern of downward
Maintained while operation gas turbine in (turndown mode) discharge standard (emission compliance) system and
Method.
Background technology
Gas turbine generating factory (such as combined cycle or combined heat and power power plant) generally includes：With compressor, combustion
The gas turbine of burner and turbine；It is arranged on the waste heat recovery steam generator (HRSG) in turbine downstream；And with HRSG fluids
The steamturbine of connection.During operation, air enters compressor via gas handling system, and is wrapped at least in part in its direction
The compressor discharge or diffuser housing of burner are little by little compressed when sending.At least a portion and fuel of the air of compression
Mixing and the burning in the combustion chamber being defined in burner, thus generate high temperature and high pressure burning gases.
Burning gases are transmitted through turbine along hot gas path from burner, and they are attached to rotor flowing through in this place
Little by little expanded during the alternate level of the static wheel blade of axle and rotatable turbo blade.Kinetic energy is transferred to turbine leaf from burning gases
Piece, therefore promote armature spindle to rotate.The rotational energy of armature spindle can be converted into electric energy via generator.Burning gases are moved back as exhaust
Go out turbine, and exhaust enters HRSG.Carry out the water that self-purging heat energy is transferred to one or more heat exchangers for flowing through HRSG,
Thus superheated steam is produced.Superheated steam is subsequently sent in steamturbine, and steamturbine can be used to generate other electric power, because
This improves overall power generation factory efficiency.
Regulatory requirements to the low emission from the power plant based on gas turbine constantly become more harsh these years.Entirely
The Environmental agencies in the world require nitrogen oxide (NOx) and other pollutions from both new and existing gas turbines now
The even lower emission level of thing and carbon monoxide (CO).In order that fuel efficiency is balanced with emission request, it is various types of
Gas turbine utilizes dry low NOx (DLN) combustion system, and it utilizes poor premixed combustion technology.
DLN-1 the or DLN-1+ type of burner of General Electric companies (Schenectady, New York)
It is two-stage premix burner, it is designed for being used together with gas fuel, thereby increases and it is possible to can be grasped using liquid fuel
Make.DLN-1 or DLN-1+ type of burner provides fuel injection system, and the fuel injection system includes being positioned at burner centre
Secondary fuel nozzle on axis, the secondary fuel nozzle is by multiple main fuel spray nozzle rings for being annularly arranged around secondary fuel nozzle
Around.During foundation load or peak load, DLN-1 or DLN-1+ type of burner may be configured to using poor premix fuel/sky
Gas is conceived to maintain low-down discharge emission level, while maintaining high-caliber efficiency.
It is generally contemplated that operator lowers gas turbine during the period when that need not generate electricity, it is thus possible to ground saving
Fuel and instantaneous recovery time when allowing to need electric power again.However, low-load level (such as during operation is adjusted)
Under, DLN-1 or DLN-1+ combustion systems usually require that heating system (inlet air bleed heating are released in air inlet
System), the downward NOx standards to realize extending.Air inlet is released heating system and adds other cost to power plant operation.Cause
This, it is desirable to provide be allowed for DLN gas turbines lower NOx emission standard air inlet release heating system elimination system and
Method.
The content of the invention
Aspects and advantages of the present invention will be illustrated in the following description, or can become obvious from description, or can be by this hair
Bright practice and acquistion.
One embodiment of the present of invention is a kind of for maintaining discharge mark while operation gas turbine in downward pattern
Accurate system.System includes gas turbine, compressor, burner, turbine and discharge section that it includes into crossfire order.Burning
Device includes being positioned at the multiple axially staged fuel injector in multiple main fuel spray nozzles and central fuel nozzle downstream.Combustion gas whirlpool
Wheel also includes deflating extracting mouth (bleed air extraction port), itself and compressor, compressor discharge housing or burning
At least one of device is in fluid communication.System also includes controller, and it is programmed for during the downward of gas turbine is operated from putting
Air lift takes the air and the multiple axially staged fuel injectors of excitation that mouth releases compression.
Another embodiment of the disclosure includes a kind of for maintaining row while operation gas turbine in downward pattern
The method for putting standard.The method includes：Burning fuel to generate the stream of the burning gases through the hot gas path of burner, its
Middle fuel is in the middle burning at least one of the main burning area of burner and secondary combustion zone, and wherein main burning area and secondary combustion zone
It is formed in the upstream of multiple axially staged fuel injectors.The method is also included from the compression for being fluidly coupled to gas turbine
At least one extraction mouth of machine, burner or turbine is extracted deflates, and the multiple axially staged fuel injectors of excitation.
First technical scheme of the invention provides a kind of maintenance while being used to operate gas turbine in downward pattern
The system of discharge standard, including：Gas turbine, compressor, burner, turbine and discharge section that it includes into crossfire order,
Wherein described burner includes being positioned at the multiple axially staged fuel in multiple main fuel spray nozzles and central fuel nozzle downstream
Injector, the gas turbine also includes deflating extracting mouth, wherein described deflation extracts mouth and the compressor, compressor discharge
At least one of housing or the burner are in fluid communication；And controller, it is programmed for the downward in the gas turbine
During operation air and the multiple axially staged fuel injector of excitation that mouth releases compression are extracted from described deflation.
Second technical scheme of the invention is that in the first technical scheme, described deflation extracts mouth via deflation air inlet stream
It is attached to the compressor and the extremely turbine body.
3rd technical scheme of the invention is that in the first technical scheme, described deflation extracts mouth via deflation air inlet stream
It is attached to the compressor and to the discharge section of waste heat recovery steam generator upstream body.
4th technical scheme of the invention is that in the first technical scheme, described deflation extracts mouth via deflation air inlet stream
It is attached to the burner and the extremely turbine body.
5th technical scheme of the invention is that in the first technical scheme, described deflation extracts mouth via deflation air inlet stream
It is attached to the burner and to the discharge section of waste heat recovery steam generator upstream body.
6th technical scheme of the invention is in the first technical scheme, also including oxidation catalyst system, wherein described
Oxidation catalyst system is arranged in the discharge section.
7th technical scheme of the invention be in the first technical scheme, also including injecting diluent system, its have with
The diluent source of supply that the hot gas path of the burner is in fluid communication, wherein the diluent source of supply will including steam,
The diluent of at least one of water or nitrogen is provided to the burner.
8th technical scheme of the invention is that in the 7th technical scheme, the diluent source of supply sprays with the main fuel
At least one of mouth fluid communication.
9th technical scheme of the invention is the main fuel spray nozzle described in the diluent source of supply in the 7th technical scheme
Downstream and the upstream end of the multiple axially staged fuel injector be fluidly coupled to the burner.
Tenth technical scheme of the invention is in the first technical scheme, also including being arranged at the import of the compressor
Multiple entry guide vanes.
11st technical scheme of the invention provides a kind of dimension while being used to operate gas turbine in downward pattern
The method for holding discharge standard, including：Burning fuel to generate the stream of the burning gases through the hot gas path of burner, wherein
The fuel in the middle burning at least one of the main burning area of the burner and secondary combustion zone, wherein the main burning area and
The secondary combustion zone is formed in the upstream of multiple axially staged fuel injectors；From being fluidly coupled to the gas turbine
At least one extraction mouth of compressor, the burner or turbine is extracted deflates；And encourage the multiple axially staged combustion
Material ejector.
12nd technical scheme of the invention be in the 11st technical scheme, also including by diluent via multiple main combustions
Material nozzle is ejected into the main burning area.
13rd technical scheme of the invention be in the 11st technical scheme, also including by diluent via center fuel
Nozzle is ejected into the secondary combustion zone.
14th technical scheme of the invention is in the 11st technical scheme, also including diluent is sprayed in center fuel
Swum out of on the downstream of mouth and the multiple axially staged fuel injector and be ejected into the hot gas path.
15th technical scheme of the invention is in the 14th technical scheme, by the injecting diluent to the hot gas
Body path includes being ejected at least one of water, steam and nitrogen in the burner.
16th technical scheme of the invention is in the 11st technical scheme, also including via being arranged under the turbine
The oxidation catalyst system of trip washs the stream of the burning gases.
17th technical scheme of the invention be in the 11st technical scheme, it is also described including the deflation is directed to
In turbine.
18th technical scheme of the invention is in the 11st technical scheme, to be also arranged on to the compression including opening
Entry guide vane at the import of machine, to increase burning gases flow rate.
After specification is read, those skilled in the art are better understood with the spy of this kind of embodiment and other embodiment
In terms of seeking peace.
Brief description of the drawings
Disclosure (including its optimal mode to those skilled in the art) that is of the invention complete and can realizing is being said
More specifically illustrated in the remainder (including refer to the attached drawing) of bright book, in the accompanying drawings：
Fig. 1 is the functional block diagram in the exemplary power plant based on gas turbine within the scope of the invention；
Fig. 2 is the simplified side cross-sectional view of the explanatory dry low-NOx combustor of at least one embodiment of the invention；With
And
Fig. 3 is there is provided the one embodiment according to the disclosure for maintaining row while operation gas turbine in downward pattern
Put a block diagram for method of standard.
List of parts
10 power plants
12 gas turbines
14 gas handling systems
16 working fluids
18 compressors
The working fluid of 20 compressions
22 fuel
24 fuel supply sources
26 burners
28 burning gases
30 turbines
32 axles
34 electrical generator/motors
36 discharge gases
38 discharge sections
40 soakers
42 HRSG
44 heat exchangers
46 steam/superheated steam
48 steamturbines
50 extract mouth
52 compressor discharge housings
54 deflation air inlets
56 oxidation catalyst systems
58 variable-angle entry guide vanes
59-99 is not used
100 DLN combustors
102 pairs/central fuel nozzle
104 main fuel spray nozzles
106 circular passages
108 stream sleeves
110 combustion liners
112 end caps/head end
114 main burning areas/premixer
116 Venturi tubes
118 secondary combustion zones
120 axially staged fuel injectors
122 transition conduits
124 hot gas paths
126 imports-turbine
128 diluent sources of supply
130 diluents
132 controllers.
Specific embodiment
Now will in detail with reference to embodiments of the invention, its one or more example is exemplified in the accompanying drawings.In detail
Explanation indicate the feature in figure using numeral and alphabetical designation.Scheme to be used to indicate with the similar or similar label in explanation
Of the invention similar or similar part.As used in this article, term " first ", " second " and " the 3rd " can be mutual
Use with changing, a component and another component are distinguished, and be not intended to represent position or the importance of single component.With
Language " upstream " and " downstream " refer to the relative direction relative to fluid stream in fluid path.For example, " upstream " refers to fluid stream side certainly
To, and " downstream " refers to the direction that fluid flow to.
Term used herein and is not intended to limit the present invention merely for the purpose of description specific embodiment.Such as at this
Used herein, singulative " ", " one " and " being somebody's turn to do " are also intended to include plural form, unless context refers to expressly otherwise
Go out.It will also be appreciated that when using in this manual, term " including " and/or "comprising" specify stated feature, whole
The presence of body, step, operation, element, and/or component, but it is not excluded for one or more other features, entirety, step, behaviour
The presence or increase of work, element, component and/or combinations thereof.
As used herein, " gas turbine load " or " load " can relate to (multiple) generator of gas turbine
Power output；" inlet guide vane angle " means axle of the import wheel blade (not shown) relative to the gas handling system through upstream of compressor
To the angle of stream；" heating is released in air inlet " means from the downstream part extraction of compressor section and is inserted into gas handling system or pressure
The upstream portion of contracting machine section is come the heat in the fluid for heating stream therein；" fuel is shared " refers to be sent in burner
The amount of the fuel of different circuit, and " emission " or " emission level " means including but not limited to nitrogen oxide (NOx), not
The level of the various exhausts of combustion hydrocarbon and carbon monoxide (CO).
Each example is provided as explanation of the invention rather than limitation of the invention.In fact, for this area
Professional is evident that, can be modified in the present invention and change without deviating from its spirit or scope.For example, making
The feature for illustrating or describing for the part of one embodiment can be used in another embodiment, to produce another embodiment.Cause
This, it is intended that is when change and change are in the range of appended claims and their equivalent, this change of present invention covering
And change.
Embodiments of the invention maintain NOx emission mark using while being used for and operate gas turbine in downward operating condition
The form of accurate system and method.In certain embodiments, present disclose provides a kind of power plant, it has compressor, pressure
At least one bypath air that the burner in contracting machine downstream is connected with compressor or burner fluid or deflate extract mouth and
In multiple fuel injectors of pair or premixed combustion area the downstream axial classification of burner.
In operation, the present invention is incorporated to the axial fuel classification combined with extraction of deflating, to disappear during operation is lowered
The need for heating is released to air inlet.Axial fuel classification enables burner to realize the NOx emission standard under lower level-off,
It is markedly inferior to the combustion gas turbine systems without axial fuel classification.Deflate and extract by making the air of compression away from burning
Device is got around with low fuel flowing level, thus prevents explosion and/or excessive supercharging, and is allowed real less than axial fuel classification institute
The additional downward of existing level.The present invention also allows entry guide vane not producing the angle of risk of icing to stay open, same with this
When allow combustion system in NOx emission standard with low-load operate.
With reference now to accompanying drawing, wherein through accompanying drawing, identical label indicates identical element, Fig. 1 to provide and produced with steam
The functional block diagram of the exemplary gas turbine generation factory 10 of raw ability.The power plant includes gas turbine 12, the gas turbine 10
Various embodiments of the present invention can be combined.As illustrated, gas turbine 12 generally includes gas handling system 14, it may include that one is
Row filter, cooling coil, water-separator, and/or other device (not shown)s are entered with purifying and otherwise adjusting
The air 16 or other working fluids of gas turbine 12.Air 16 flows to compressor section, here, compressor 18 is progressively right
Air 16 applies kinetic energy, to produce such as the air of the compression schematically indicated by arrow 20.
The air 20 of compression mixes with the fuel 22 (such as natural gas) from fuel system 24, with one or more
Flammable mixture is formed in multiple burners 26.The flammable mixture is incinerated to produce with high temperature, high pressure and two-forty
The burning gases for such as schematically being indicated by arrow 28.Burning gases 28 flow through the turbine 30 of turbine, to produce work(.Example
Such as, turbine 30 may be connected to axle 30 so that the rotation driving compressor 18 of turbine 30 is producing the air 20 of compression.Alternatively or
Additionally, turbine 30 can be connected to generator 34 for producing electricity by axle 32.
Discharge gas 36 from turbine 30 flows through discharge section 38, and discharge section 38 connects as turbine 30 turbine 30
The soaker 40 in downstream.Discharge section 38 may include such as waste heat recovery steam generator (HRSG) 42, for discharging extremely
Discharge gas 36 is cleaned before environment and extra heat is extracted from discharge gas 36.For example, HRSG42 may include it is one or more
Individual heat exchanger 44, one or more heat exchangers 44 are such as illustrated with the discharge thermal communication of gas 36 and can generating by arrow 46
Steam or superheated steam that ground is indicated.Then steam 46 can be sent to the various components at power plant 10, such as to one or
More steamturbines 48 and/or extremely various heating system (not shown).
In various embodiments, gas turbine 12 may include that one or more deflation or bypath air extract mouth 50.
In specific embodiment, as shown in fig. 1, at least one deflation is extracted mouth 50 and is provided on compressor discharge or diffuser housing 52
The free flow path for driving compressor 18.In a particular embodiment, as shown in fig. 1, at least one deflation is extracted mouth 50 and is provided
Leave the flow path of compressor discharge housing 52.In a particular embodiment, (multiple) deflation is extracted mouth 50 and can be used to such as exist
The pressure in burner 26 is reduced during non-premixed mode of operation.In various embodiments, gas turbine 12 may include at least one
Individual deflation or bypath air air inlet 54.
Extraction mouth 50 of deflating can be in fluid communication with various external members.For example, in one embodiment, at least one deflates
Extracting mouth 50 can fluidly connect via various fluid conduit systems, connector, valve and/or at least one deflation air inlet 54 with turbine 30
It is logical.In this way, a part for the air 20 of the compression from compressor 18 and/or compressor discharge housing 52 may be sent to that turbine
30, the various components of turbine 30 are cooled to provide, and/or reduce the pressure in burner 26 and/or compressor discharge housing 52
Power.In a particular embodiment, at least one deflation extraction mouth 50 can be via various fluid conduit systems, connector, valve and/or at least one
Individual deflation air inlet 54 is fluidly connected in the upstream of HRSG42 with discharge section 38.In this way, from compressor 18 and/or compression
A part for the air 20 of the compression of machine discharge housing 52 may be sent to that discharge section 38, to provide heat energy changing to HRSG42
Hot device 44 and/or offer are cooled to the various components of discharge section 38, and/or reduce burner 26 and/or compressor discharge shell
Pressure in body 52.
In a particular embodiment, oxidation catalyst module or system 56 can be positioned on downstream and the soaker 40 of turbine 30
Upstream.Oxidation catalyst system 56 can be used to reducing or possibly eliminating the oxidation for being included in stream from the exhaust 36 of turbine 30
Carbon (CO), unburned hydrocarbon or other undesirable emissions.
In various embodiments, compressor 18 includes that the multiple variable-angle imports being arranged at the import of compressor 18 are led
Leaf 58.Stator 58 can rotate around longitudinal axis between the open and closed positions.The angle of entry guide vane 58 can be changed
To meet the air flow demand of engine operating condition.For example, entry guide vane 58 can close or close at least in part with
Limited to the air stream of compressor 18 and burner 26 in engine start and during low-load or low RPM.Entry guide vane 58
Can little by little be opened to increase to the air stream of compressor 18 and/or burner 26 when load or RPM increase.Start or
During low-load condition, the angle of attack angulation of entry guide vane 58 is to avoid making the stall of compressor 18.
In various embodiments, burner 26 is dry low NOx (DLN) type of burner.Fig. 2 is provided can be replaced as schemed
Burner 26 shown in 1 is attached to the simplified side cross-sectional view of the exemplary DLN types burner 100 of gas turbine 12.In spy
Determine in embodiment, as shown in Figure 2, burner 26 is by General Electirc companies (Schenectady, New
York) DLN-1 the or DLN-1+ types burner 100 of manufacture.Fuel injection system for burner 100 is fired including Fu Huo centers
Material nozzle 102 and around central fuel nozzle 102 radially and multiple main fuel spray nozzles 104 for circlewise organizing.In operation,
A part for the air 20 of the compression from compressor (Fig. 1) is directed across from compressor discharge housing 52 and is limited to stream sleeve
Annular flow passage 106 between 108 and one or more combustion liners 110.The air 20 of compression is at the end of burner 100
Flow direction is overturned at lid or head portion 112 and main fuel spray nozzle 104 and central fuel nozzle 106 is flowed through, or in main fuel
Nozzle 104 and the surrounding of central fuel nozzle 106 flow.
As shown in Figure 2, DLN combustor 100 includes main burning area or premixer 114, and it is formed in each main fuel spray nozzle
104 downstream and the upstream of Venturi tube 116, the Venturi tube 116 is at least in part by one or more in combustion liner 110
Formed.Burner 100 also includes secondary or premixed combustion area 118, and secondary or premixed combustion area 118 is limited under main burning area 114
Trip and the downstream of central fuel nozzle 102.Main fuel spray nozzle 104 and central fuel nozzle 102 are via various fluid conduit systems, flow
Control valve and/or connector are fluidly connected with fuel system 24.
Fuel system 24 may be configured to provide identical fuel type (such as natural gas or liquid fuel) to main combustion
Both material nozzle 104 and central fuel nozzle 106.In some configurations, fuel system 24 may be configured to provide different
Fuel type (such as natural gas and/or liquid fuel) is to main fuel spray nozzle 104 and/or central fuel nozzle 102.
During operation, burner 100 is operated and the transition between various operator schemes in various operator schemes.These
Operator scheme relates generally to load and/or power plant 10 required the steam output being placed on gas turbine.As in Fig. 2
Shown DLN types burner 100 generally depends on load level and/or the required steaming in power plant 10 of the demand of gas turbine 12
Vapour output carrys out operation or transition between principal mode, lean-lean operator scheme, secondary operator scheme and premixed mode of operation.Such as
It is used in the present context, term " non-premixed mode of operation " refers to that any one of main, lean-lean or secondary operator scheme arrives premixed
Transition point burner 100 operator scheme.Additionally, " non-premixed mode of operation " may include in master, lean-lean and secondary operation mould
Any transient operation pattern occurred between formula.
Principal mode is generally from 30 about percent generation lighted to full load.During principal mode,
Fuel system 24 provides 1 percent hundred to the main fuel spray nozzles 104 to the total fuel flow of burner 100.As a result, main behaviour
Burning during operation mode is mainly carried out in main burning area 114.Principal mode is used in low-load to middle load, until in advance
Gas turbine 12 is lighted, accelerates and operated in the range of the combustion reference temperature of choosing.
Lean-lean operator scheme is generally in 70 30 about percent to about percent generation from full load.It is poor-
During poor operation, fuel system 24 shares total fuel flow between main fuel spray nozzle 104 and central fuel nozzle 102.Example
Such as, fuel system 24 can provide about 7 percent ten to main fuel spray nozzles 104 of total fuel flow, and provide total fuel flow
About 3 percent ten to central fuel nozzles 102.As a result, the burning during lean-lean operator scheme main burning area 114 with
And carried out in secondary both combustion zones 118.The intermediate loads that the operator scheme is used between two pre-selection combustion reference temperatures.
Secondary operator scheme is generally sent out when when the transition between lean-lean operator scheme and premixed mode of operation of burner 100
It is raw.During secondary operator scheme, fuel system 24 can near main fuel spray nozzle 104 The fuel stream to burner 100
70 about percent reduction of total fuel flow to about 0 percent, while the The fuel stream of near central fuel nozzle 102 from
30 about the percent of total fuel flow is improved to 100 about percent, so as to allow the flame related to main burning area 114
Extinguish, while being derived from the flame of central fuel nozzle 102 in maintaining secondary combustion zone 118.The pattern is for extinguishing main burning area 114
In flame be necessary.
When being operated in the premixed mode of operation of burner 100, between main fuel spray nozzle 104 and central fuel nozzle 102
Fuel share and can change so that main fuel spray nozzle 104 is received to 80 about the percent of the total fuel flow of burner 100,
And central fuel nozzle 102 can be received to 20 about the percent of the total fuel flow of burner 100.It flow to main fuel spray nozzle
Pressure of 102 fuel 22 in main burning area 114 (it is in this main pre-mix zone 114) and from compressor reducer 18 (Fig. 1)
The air 20 of contracting is premixed, and fuel/air mixture is formed with main burning area 114.The fuel/air mixture of poor premix is right
After flow through Venturi tube 116 and in secondary combustion zone 118, it is by the flame ignition from central fuel nozzle 102 in this place.The behaviour
Operation mode is in and is realized close to combustion reference temperature design point.Optimal emission is generated in premixed.
The loading range associated with master, lean-lean, secondary and premixed mode of operation can be from the model provided above based on various factors
Enclose transfer.For example, loading range can with entry guide vane (IGV) adjust degree and (to a lesser extent) with air 16
Environment temperature and change.For example, under ISO environment, premixed mode of operation opereating specification can be with IGV adjustment downwards to about 42 °
And from about 50% to 100%, and with IGV adjustment downwards to about 57 ° from about 75% to 100%.On various operator schemes
It is exemplary that various fuel are shared provided herein, and is not intended to be restricted, unless specified in addition in the claims.
In a particular embodiment, as shown in FIG. 2, burner 100 includes multiple axially staged fuel injectors 120
(also referred to as postpone poor oil ejector (LLI:Late Lean Injector)), it is surround from the downstream of (multiple) combustion liner 110
The transition conduit 122 of extension is annularly arranged.(multiple) combustion liner 110 and transition conduit 122 at least partially define through
The hot gas path 124 of burner 100, its import 126 (Fig. 1) for extending to turbine.Fuel injector 120 is provided through transition
Pipeline 122 is to the fluid communication in hot gas path 124.Fuel injector 120 can be extended to different radial depths
Cross in pipeline 122 and/or hot gas path 124.
In fuel injector 120 each or at least some may be configured to provide that time delay is oil-poor or axial fuel classification energy
Power is to burner 100.That is, fuel injector 120 is individually configured to fuel and/or fuel/air mixture along generally horizontal
Hot gas path 124 is supplied to the direction in the leading flow direction of the burning gases 28 for flowing through hot gas path 124.
In the case of this, the condition in burner 100 and hot gas path 124 is classified into the partial zones for creating stabilization burning, while reducing
The formation of NOx emission, therefore improve the overall performance of burner 100.
In various embodiments, as shown in Figure 2, burner 100 can be fluidly coupled to diluent source of supply 128.It is dilute
Releasing agent source of supply 128 can provide such as steam, water in the upstream or downstream of main fuel spray nozzle 104 and/or central fuel nozzle 102
Or the diluent 130 of nitrogen is to burner 100.For example, in a particular embodiment, diluent source of supply 128 may be configured in pair
The downstream of combustion zone 118 and diluent 130 is directly injected to hot gas path 124 in the upstream of multiple fuel injectors 120
In.In a particular embodiment, diluent source of supply 128 may be configured to diluent 130 at main fuel spray nozzle 104 and/or center
The injected upstream of fuel nozzle 102 is in fuel 22.Diluent 130 can be used for during the non-premixed mode of operation of premix and/
Or NOx emission level is reduced during foundation load, peak load or low-load operating condition and/or burner is improved
Energy.
As jointly shown in Fig. 1 and 2, fuel system 24, diluent source of supply 128 and/or HRSG42 can electronics
Be attached to controller 132.Controller 132 can be programmed to be based at least partially on gas turbine load and/or power plant 10
Steam demand is with the flow rate that is similar to and guides fuel system 24 to supply or share with different flow rate to flow to main fuel and spray
The fuel 22 of mouth 104 and central fuel nozzle 102.
Controller 132 may be incorporated into General Electric SPEEDTRONICTMGas turbine control system, such as exists
" the SPEEDTRONIC Mark V Gas Turbine Control System (SPEEDTRONIC of Rowen, W. I.
Mark V gas turbines control system) " (GE-3658D, by Schenectady, the GE Industrial ＆ Power of N.Y
Systems is issued) described in.Controller 132 can also be incorporated into the computer system with (multiple) processor, and processor is held
Row storage program in memory is being input into using sensor and instruction from human operator who controls gas turbine
Operation.The program performed by controller 132 may include dispatching algorithm, dilute to the The fuel stream of burner 100, regulation for adjusting
Release the flowing, regulation of agent 130 to burner 100 deflation or bypass from compressor 18 and/or compressor discharge housing 52 empty
Gas, the angle of entry guide vane 58, steam output and the emission related for reducing burning.The order produced by controller 132
Valve can be promoted to actuate between the open and closed positions, to adjust fuel, deflation and the flowing of diluent, and also promote actuator
Adjust the angle of entry guide vane 58.
Controller 132 can be based at least partially on the database being stored in the memory of controller 132 and carry out regulating gas
Turbine 12.The database can enable controller 132 during operation is lowered by the NOx and CO in gas turbine discharge section 38
Emission is maintained in a certain predetermined limitation, to maintain predetermined steam to export, and burner 100 is maintained suitable steady
In fixed limit circle.The settable such as gas turbine load of controller 132, steam production demand, deflation flow rate, the flowing of diluent and
The operating parameter that burner fuel is shared, so as to：1) operated and/or at unloaded full gear (FSNL) in non-premix or downward pattern
Condition is until while operation between foundation load condition, realize desired emission level；2) eliminate simultaneously and air inlet is released
The demand of heating.
During foundation load or peak load, burner 100 is operated in premixed.In the phase of the operator scheme
Between, emission level is generally maintained in desired acceptable emission level, and HRSG42 operation be optimised with
Sufficient steam stream is provided to drive steamturbine 48 and/or support various secondary operations.It is (all during off-peak load demand
Such as during operation is lowered), operator can wish to operate gas turbine to reduce the required time, so that gas turbine returns to connection
Machine is for generating.However, during the downward of gas turbine 12 is operated, emission level increases.Therefore, in order to reduce discharge
Thing level, operator generally by the injected upstream deflated in compressor to blow-off system to improve the intake air temperature of air 16, by
This reduces the formation of NOx.
However, in various embodiments such as presented herein, during operation is lowered, operator can (manually or warp
By controller 132) via one or more by the air 20 for compressing from compressor 18 or compressor in extraction mouth 50 of deflating
At least one of discharge housing 52 is released, thus the pressure of the air 20 of the compression in reduction burner 100, and is therefore prevented
Flame blow-off and stabilization combustion flame.Meanwhile, fuel injector 120 can be energized and be sprayed with by fuel or fuel/air mixture
It is mapped in burning gases 28, to reduce NOx emission.In this way, during non-premixed mode of operation and/or lowering the operation phase
Between do not need inlet air heating NOx emission is maintained into standard level.Deflation may be sent to that gas handling system 14, turbine 30 or
At least one of discharge section 38.In a particular embodiment, deflate and can be used to heat energy is added into row in the upstream of HRSG42
Gas 36.
In a particular embodiment, diluent 130 (that is, steam, water, nitrogen etc.) can fire in main fuel spray nozzle 104 and center
The injected upstream of nozzle 102 is expected to fuel 22, and/or can be ejected into hot gas path 124 via diluent source of supply 128
In burning gases 28, to reduce the NOx output in hot gas path 124.In addition, fuel injector 120 can by fuel or fuel/
Air mixture secondary combustion zone 118 downstream injection in hot gas path 124, therefore reduce the NOx in burning gases 28.
Oxidation catalyst system 56 is can trigger to come when discharge gas 36 flow through discharge section 36 towards soaker 40 less than basis
Further reduce various undesirable emissions, such as carbon monoxide in the downstream for premixing pipeline incinerator 60 under loading condition
(CO).In this configuration, the aspiration level of the steam output from power plant 10 can be maintained, at the same less than foundation load or
Mitigate emission level under non-premixed operation condition (during such as gas turbine is lowered).
Various embodiments described herein and accompanying drawing are provided for lowering the same of mode of operation gas turbine
When maintain discharge standard one or more methods.Fig. 3 is there is provided the one embodiment according to the disclosure for lowering
A block diagram for method 200 of discharge standard is maintained while mode of operation gas turbine.As shown in Figure 3, in step
202, method 200 includes burning fuel 22 to generate the stream of the burning gases 28 through the hot gas path 124 of burner 100,
Wherein fuel 22 is in the middle burning at least one of the main burning area 114 of burner 100 and secondary combustion zone 118, and wherein main combustion
Burn area 114 and secondary combustion zone 118 is formed in the upstream of multiple axially staged fuel injectors 120.In step 204, method 200
Deflated including being extracted from least one extraction mouth 50 for being fluidly coupled to compressor 18, compressor discharge housing 52 or turbine 30
Or the air 20 of compression.At step 206, method 200 includes the multiple axially staged fuel injectors 120 of excitation.
In a particular embodiment, method 200 may include diluent 130 via one of multiple main fuel spray nozzles 104 or
More main fuel spray nozzles 104 are ejected into main burning area 114.In a particular embodiment, method 200 may include diluent
130 are ejected into secondary combustion zone 118 via central fuel nozzle 102.In a particular embodiment, method 200 may include to dilute
Agent 130 is ejected into hot gas in the downstream of central fuel nozzle 102 and in multiple axially staged upstream ends of fuel injector 120
In path 124.In a particular embodiment, diluent 130 is ejected into hot gas path 124 is included water, steam and nitrogen
At least one of be ejected into burner 100.
In a particular embodiment, method 200 may include via the oxidation catalyst system 56 for being arranged on the downstream of turbine 30
Wash the stream of burning gases 28.In a particular embodiment, method 200 may include to be directed to deflation 20 in turbine 30.Specific
In embodiment, method 200 may include to open entry guide vane 58 to increase burning gases flow rate.
Although illustrating and describing specific embodiment herein, it will be appreciated that being considered as realizing identical mesh
The replaceable shown specific embodiment of any arrangement, and the present invention is with the other application in other environment.The application
It is intended to covering any remodeling of the invention or deformation.Appended claims are in no way intended to limit the scope of the invention to herein
The specific embodiment of description.
Claims (10)
1. it is a kind of in downward pattern operate gas turbine while maintain discharge standard system, including：
Gas turbine (12), compressor (18), burner (26), turbine (30) and discharge section that it includes into crossfire order
(38), wherein the burner (26) is including being positioned at multiple main fuel spray nozzles (104) and central fuel nozzle (102) downstream
Multiple axially staged fuel injectors (120), the gas turbine (12) also includes deflate (20) extraction mouth (50), wherein institute
State deflation (20) extract mouth (50) with the compressor (18), compressor discharge housing (52) or the burner (26) in extremely
A few fluid communication；And
Controller (132), it is programmed for extracting mouth from the deflation (20) during the downward of the gas turbine (12) is operated
(50) release the air (20) of compression and encourage the multiple axially staged fuel injector (120).
2. system according to claim 1, it is characterised in that the deflation (20) extract mouth (50) via deflate (20) enter
Gas port (54) is fluidly coupled to the compressor (18) and the extremely turbine (30).
3. system according to claim 1, it is characterised in that the deflation (20) extract mouth (50) via deflate (20) enter
Gas port (54) is fluidly coupled to the compressor (18) and to the discharge area of waste heat recovery steam generator (42) upstream
Section (38).
4. system according to claim 1, it is characterised in that the deflation (20) extract mouth (50) via deflate (20) enter
Gas port (54) is fluidly coupled to the burner (26) and the extremely turbine (30).
5. system according to claim 1, it is characterised in that the deflation (20) extract mouth (50) via deflate (20) enter
Gas port (54) is fluidly coupled to the burner (26) and to the discharge area of waste heat recovery steam generator (42) upstream
Section (38).
6. system according to claim 1, it is characterised in that also including oxidation catalyst system (56), wherein the oxygen
Change antigravity system (56) to be arranged in the discharge section (38).
7. system according to claim 1, it is characterised in that also including injecting diluent system (128), it has and institute
The diluent source of supply that the hot gas path (124) of burner (26) is in fluid communication is stated, wherein the diluent source of supply will be wrapped
The diluent (130) for including at least one of steam, water or nitrogen is provided to the burner (26).
8. system according to claim 7, it is characterised in that the diluent source of supply and the main fuel spray nozzle
At least one of (104) fluid communication.
9. system according to claim 7, it is characterised in that the diluent source of supply is in the main fuel spray nozzle
(104) downstream and the upstream end of the multiple axially staged fuel injector (120) is fluidly coupled to the burner
(26)。
10. system according to claim 1, it is characterised in that also including being arranged at the import of the compressor (18)
Multiple entry guide vanes (58).
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201562210636P | 2015-08-27 | 2015-08-27 | |
| US62/210636 | 2015-08-27 | ||
| US15/237,726 US20170058784A1 (en) | 2015-08-27 | 2016-08-16 | System and method for maintaining emissions compliance while operating a gas turbine at turndown condition |
| US15/237726 | 2016-08-16 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106762158A true CN106762158A (en) | 2017-05-31 |
| CN106762158B CN106762158B (en) | 2020-07-07 |
Family
ID=58097707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610743517.9A Expired - Fee Related CN106762158B (en) | 2015-08-27 | 2016-08-29 | System and method for operating a gas turbine while maintaining emissions standards |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20170058784A1 (en) |
| JP (1) | JP2017044209A (en) |
| CN (1) | CN106762158B (en) |
| IT (1) | IT201600087600A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111980804A (en) * | 2020-08-24 | 2020-11-24 | 广州沐风信息科技有限公司 | Gas turbine power generation equipment |
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| WO2018106991A1 (en) * | 2016-12-09 | 2018-06-14 | Powerphase Llc | Air logic control for auxiliary air injection system |
| US10502145B2 (en) * | 2017-07-10 | 2019-12-10 | Hamilton Sundstrand Corporation | Integrated fuel and bleed system control architecture |
| GB201818014D0 (en) | 2018-11-05 | 2018-12-19 | Rolls Royce Plc | Control system for a gas turbine engine |
| US11384940B2 (en) | 2019-01-23 | 2022-07-12 | General Electric Company | Gas turbine load/unload path control |
| US11280496B2 (en) * | 2020-03-25 | 2022-03-22 | General Electric Company | Gas turbine engine and methods of controlling emissions therefrom |
| US11203986B1 (en) * | 2020-06-08 | 2021-12-21 | General Electric Company | Systems and methods for extended emissions compliant operation of a gas turbine engine |
| US11898502B2 (en) * | 2020-12-21 | 2024-02-13 | General Electric Company | System and methods for improving combustion turbine turndown capability |
| US11846426B2 (en) * | 2021-06-24 | 2023-12-19 | General Electric Company | Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel |
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Also Published As
| Publication number | Publication date |
|---|---|
| IT201600087600A1 (en) | 2018-02-26 |
| CN106762158B (en) | 2020-07-07 |
| US20170058784A1 (en) | 2017-03-02 |
| JP2017044209A (en) | 2017-03-02 |
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